Similarly shaped airfoils to NACA65-318 a=0.8
New! Bulk download of polars in Excel format: NACA65-318%20a%3D0.8.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. NACA65-318 a=0.6
3. GA 40-218
4. NACA65-318
5. NACA64A318
6. GA 40A218
7. NACA65-318 a=0.5
8. NACA63A318
9. NACA65-319 a=0.8
10. NACA65-317 a=0.8
11. GA 37A218
12. NACA65-419
13. NACA65-417
14. NACA64A317
15. NACA64-318 a=0.8
16. NACA65-317 a=0.6
17. NACA65-319 a=0.6
18. NACA64-418
19. NACA65A318
20. GA 40-217
21. GA 35A218